THRUST REVERSER AND THRUST REVERSING METHOD

Japanese Patent JP2017002890

A

PROBLEM TO BE SOLVED: To provide a thrust reverser that is improved in compliance with composing elements of the thrust reverser adapted for an efficiency of an aircraft and its performance requirement.SOLUTION: A thrust reverser 28 is adapted to be fixed in an engine nacelle 14 extending around a cowl 18. The nacelle 14 and the cowl 18 integrally define a duct 22 extending axially to receive bypass air flow 32 flowing rearward. The air flow 32 changes its direction to a forward direction when the reverser 28 is developed. The nacelle 14 includes a sleeve advancing in its axial direction, a translation cascade set 20 arranged in a peripheral direction and a blocker door 40 pivoted from the translation sleeve in a radial inner direction that is translatable in an axial direction and adapted to extend partially in an air flow 32. A door developing drug link mechanism 42 is pivotally connected to each of the translation sleeve and the door 40. When it is stored, an outer wall 50 extending in an axial direction of the duct 22 is held between the door 40 and the air flow 32 in a radial direction and it is assured that the door 40 is kept at a state in which it is completely shielded against the air flow 32.SELECTED DRAWING: Figure 2

WO/2017/134402	AIRCRAFT PROPULSION UNIT
WO/2024/023432	THRUST REVERSER COMPRISING AN IMPROVED SYSTEM FOR TRANSLATABLY ACTUATING THE MOVABLE STRUCTURE OF THE REVERSER
WO/2011/135238	TURBOJET ENGINE NACELLE

DAVID W FOUTCH

JP2016039744A

January 05, 2017

March 02, 2016

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BOEING CO

F02K1/72

Yasuhiko Murayama
Tatsuhiko Abe
Kuroda Shinpei
Choi

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